小型飞机起落架电动作动筒结构优化

Structure Optimization of Electromechanical Actuator for Light Aircraft Landing Gear

为了取代传统的液压收放系统,实现小型飞机的全电动控制,设计了一种电动作动筒。该作动筒具有直线收放、到位时锁定、收放时解锁和故障时应急放的功能。利用有限元仿真方法对上锁状态下作动筒的强度和刚度进行校核分析,在此基础上对作动筒结构参数进行优化设计,从而获得更加合理的结构尺寸和更高的强度。

In order to replace traditional hydraulic actuation system and make light aircraft all-electrically, a electromechanieal actuator（EMA） is developed. The EMA has linear extension and retraction, lock and unlock, emergency extension capability. The finite element analysis method is presented to check the strength and rigidity of the EMA. On that basis, the structure of the EMA is optimized, and more reasonable sizes and higher strength are obtained.